Radome cover shell and opening kinematic

ABSTRACT

An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail. The radome shell opening kinematic further comprises a radome cover shell rotation stopper that can stop movement of the radome cover shell at the completely opened position.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.17/077,573 filed Oct. 22, 2020, the disclosure of which is herebyincorporated in its entirety by reference herein.

BACKGROUND OF THE INVENTION (1) Field of the Invention

The present embodiments relate to an aircraft with an aircraftstructure, and, more particularly, to an aircraft with an aircraftstructure that comprises a radome cover shell and opening kinematic.

(2) Description of Related Art

A radome is usually located at the nose region of an aircraft andincludes equipment that is located in that particular region of theaircraft and a radome cover. The radome cover is a compound curved shellstructure used to enclose or protect the equipment housed in the noseregion of the aircraft. Radome covers can be formed in a variety ofshapes, depending upon the type of aircraft with which the radome coveris being used. One common shape is the approximately conical shape seenon numerous jet aircraft or helicopters. The conical shape isoccasionally supplemented with a pointed or needle-like projectionextending beyond the conical shape.

A radome cover usually includes a radome cover shell and a radome coveropening kinematics. The radome cover shell is conventionally attached tothe aircraft structure by means of the radome cover opening kinematics,and the radome cover opening kinematics should provide easy access tothe enclosed equipment. The radome cover opening kinematics ofteninclude fixed hinges that attach the radome cover shell to the aircraftstructure. However, conventional hinge mechanisms with a simple rotationaround a fixed axis would interfere with the enclosed equipment duringthe rotational movement.

Therefore, most radome cover opening kinematics slide the radome covershell forward before rotating it around a fixed axis. As an example, theH155 helicopter of Airbus Helicopters has an opening mechanism thatinvolves a sliding mechanism with a rod that can be moved along the rodaxis within a guiding tube and a hinge that is attached to the radomecover shell and the middle of the rod. During the opening operation, therod has to be pulled out of the guiding tube with a sliding movementuntil the hinge is free to rotate. The following rotation then swivelsthe radome cover shell upwards. During the closing operation, the radomecover shell is rotated downwards before the rod can be pushed back intothe guiding tube with a sliding movement.

However, sliding mechanisms are usually sensitive to dirt and have to beadjusted precisely during installation to avoid twisting and blocking ofthe rod inside the guiding tube. Furthermore, the above describedsliding mechanism introduces high bending moments and loads into theguiding tube when the rod is pulled out of the guiding tube. Thus, alightweight design of the sliding mechanism with the rod and the guidingtube is difficult to achieve and requires a lot of space.

The document CN 207565827U describes a radome coupling mechanism. Itincludes a radome cover, a hinge, a hook lock, and a vaulting pole. Theradome cover is arranged at the front of the fuselage. It provides anopening part that can seal the opening. The radome cover is passedthrough the hook lock near one side of ventral and is connected with thefuselage. The vaulting pole is arranged inside the fuselage and its oneend is connected with the radar mounting platform, the other end isconnected with the radome cover. The vaulting pole is provided with aself-lock device. The vaulting pole length remains unchanged through theself-lock device after a complete opening of the radome cover.

Thus, the document discloses a radome cover that is easily dismountable.However, the radome cover is not a complete dome, but rather a half-domeand/or the aircraft has no equipment installed at the forefront of thedome. Thus, the radome cover can perform just a simple rotation withouta forward longitudinal movement.

Other state-of-the-art includes radome covers with an opening kinematicsthat performs a simple rotation or a rotation after a longitudinalmovement involving a rod.

For example, the document U.S. Pat. No. 9,608,320 B2 describes a methodfor opening a dome for the protection of a device to be protected,fitted in a part described as fixed, in which, in the initial positionbefore opening, a generally plane interface separates the dome from thefixed part. The method includes connecting the dome to the fixed part byat least two independent double-link connections that are movable inrotation between the dome and the fixed part. The links in a singleconnection being fitted in common to the dome and to the fixed part toform overall a pantograph in the shape of an isosceles trapezium which,during opening, opens out by pivoting until maximum opening is achieved,so that the dome moves away from the fixed part via a combination ofmovements in translation and in rotation.

In fact, a connecting pair and two telescopic rods are fixed, at theirextremities, to the inner rim of the radome cover and to the face of theradome cover via appropriate hinges and for connection in rotation. Eachtelescopic rod is positioned vertically to the common fitting of thecorresponding connecting pair at a distance greater than the length ofthe pair. In addition, by virtue of the positioning on a common fittingand at the periphery of the radome, each connecting pair is shorter thanthe corresponding telescopic rod. Furthermore, the telescopic rods havean automatic locking position corresponding to the maximum finalopenness of the radome relative to the face of the fuselage.

Document U.S. Pat. No. 6,796,529 B1 describes a strut for propping openthe door of an aircraft including an outer tube connected at one end tothe aircraft and a telescoping inner member connected to the aircraftdoor. The inner member is extended out of the outer tube when the dooris fully opened and automatically locks in place. The strut can beunlocked by grasping a sleeve mounted on the outer tube, pulling itdownwardly while rotating the same clockwise. The strut remains lockeduntil the door is lifted upwardly until it stops thereby unlocking thestrut. Lowering the door returns the strut to its stowed position withthe inner member received within the outer tube.

Document U.S. Pat. No. 5,820,077 A describes a radome structure havingan integrally attached attaching structure for attachment to anaircraft, the attaching structure being affixed to a rearward portion ofthe radome.

Document U.S. Pat. No. 2,943,756 A describes a radome cover of generallyhemispherical configuration that is pivotally mounted on the body of anairplane at its upper marginal edge by a usual double-leaf hinge havingone of its leaves secured to the radome cover and the other to the bodyof the airplane as by nuts and bolts or in any other conventionalfashion. Carried by a shaft are two triangular truss assemblies, eachassembly formed of a pair of braces, which extend from connections withtorque shaft at their inner ends to join at an apex. The braces aresecured to each other at the V-shaped juncture of their outerextremities as by welding and are secured to the torque shaft as bywelding, for common movement therewith. As shown, in their connection tothe torque shaft, a first brace will be located on one side of a bearingblock and a second brace on the opposite side. At the V-shaped junctureof each of the truss assemblies there is formed a slot within which issecured, as by welding, a plate. Each of the pair of plates extendsbeyond the outer end of its truss and projects into a space providedbetween a pair of track-engaging or slide members, and each is pivotallyconnected to its associated pair of members by a bolt and nut.

The document US2017062920 describes a radome that covers a radar systempositioned under the fuselage of a fixed wings aircraft. The radarsystem is positioned within an internal volume of a shell in which isforming the radome covering the radar system. A track attached to theradome is engaged with a corresponding track attached to the aircraftstructure, for a sliding mutual engagement. Bearings as roller balls orball bearings, are positioned relatively the tracks so as to allowrectilinear sliding of the radome. Only when slid to an axially extendedposition the radome can possibly reach an expanded position. When inexpanded position, articulated arms can be oriented at an angle withrespect to the axial direction of the tracks. This is to give the radomea fully unwrapped position. Some bearings are provided on opposing sidesof the guiding rail.

The document U.S. Pat. No. 3,374,972 describes a door for the cargocompartment of an aircraft, which forms an aerodynamic aft portion offuselage and swings vertically in visor fashion from the fuselage to anoverhead position. The door is articulated to the fuselage by hinges. Afree end of the door is connected to the fuselage through power actuatormeans. Also, symmetrically disposed on each side of the fuselage arefixed hinge connections in the form of pivots, which are secured tostructure of the aircraft. The door is also connected to stationaryaircraft structure by a mechanism capable of forcibly driving in variouspositions. Internally the door carries a fixed structural rib that iscurved describing an arc of a circle drawn about the hinge connections.This structural rib is secured to inner surface of the door and to anouter surface aircraft structure, via a bulkhead. The structural ribcarries a gear track on each side, for constant meshing coaction with adrive gear projecting from a wall of the structure. The gears aresymmetrically disposed about the transverse center of the aircraft andare driven in unison in opposite directions by conventional drivingmeans inside the aircraft. Parallelly disposed on the rib adjacent eachtrack is a guide to engage a pair of rollers that straddle each gear.Each pair of rollers are carried by a support secured to and projectingfrom the structure, whereby to ensure the constant engagement of thegears in their respective tracks and to prevent relative lateralmovement of the door during its vertical swinging movement.

The documents CN207565827, FR2379434 or U.S. Pat. No. 4,174,609 andDE1481684 were also cited.

In summary, many state-of-the-art aircrafts have radome covers withradome cover shells and radome cover opening kinematics that use hingesonly for a rotational movement or hinges combined with rods for alongitudinal movement followed by a rotational movement during theopening of the radome cover shell and a rotational movement followed bya longitudinal movement during the closing of the radome cover shell.Radomes having radome covers with radome cover opening kinematics thatomit a longitudinal movement cannot house equipment at the forefront ofthe radome, thereby wasting space. Radomes having radome covers withradome cover opening kinematics that perform a longitudinal movementoften rely on a sliding mechanism involving rods within guiding tubes toperform the longitudinal movement.

However, as mentioned above, such a sliding mechanism is sensitive todirt and has to be adjusted precisely during installation to avoidtwisting and blocking of the rod inside the guiding tube. Furthermore,the sliding mechanism introduces high bending moments and loads into theguiding tube when the rod is pulled out of the guiding tube. Thus, alightweight design of the sliding mechanism with the rod and the guidingtube is difficult to achieve and requires a lot of space.

BRIEF SUMMARY OF THE INVENTION

It is, therefore, an objective to provide an aircraft with a new radomecover shell and opening kinematic. The new radome cover shell andopening kinematic should have a lightweight design, require littlespace, and be robust, easy to install, and comparably insensitive todirt.

The objective is solved by an aircraft comprising the features of claim1. More specifically, an aircraft with an aircraft structure maycomprise a radome cover shell and a radome cover shell openingkinematic. The radome cover shell may be adapted to enclose equipment ina nose region of the aircraft in a closed position. The radome coveropening kinematic may enable a first movement of the radome cover shellfrom the closed position to an opened position and a second movement ofthe radome cover shell from the opened position to the closed position.The radome cover opening kinematic comprises a guiding rail that isattached to the radome cover shell, and at least three rollers that areattached to the aircraft structure, wherein a first and a second rollerof the at least three rollers are arranged on opposing sides of theguiding rail, and wherein the second and a third roller of the at leastthree rollers are arranged on the same side of the guiding rail. Thefirst movement of the radome cover shell from the closed position to theopened position comprises a longitudinal movement from the closedposition to a first partially opened position, a first rotationalmovement from the first partially opened position to a second partiallyopened position, and a second rotational movement from the secondpartially opened position to a completely opened position, wherein theradome shell opening kinematic further comprises a radome cover shellrotation stopper that stops the second rotational movement of the radomecover shell at the completely opened position.

Illustratively, the radome cover opening kinematic comprises a rail thatis installed at the radome cover shell and is guided by rollers that areinstalled on the airframe structure.

The radome cover opening kinematic allows a sequential longitudinalmovement and a rotational movement of the radome cover shell during theopening of the radome cover shell to avoid contact with equipment thatis installed in the recess of the aircraft and covered by the radomecover shell when the radome cover shell is in the closed position.

Thus, any longitudinal movement of the radome cover shell is guided byrollers and not by sliding. For that purpose, three rollers guide amotion link with a rail. The motion link is movable and fixed to theradome cover shell while the rollers remain in their position.

The rollers reduce the friction and ensure a smooth motion during thelongitudinal movement. The distance between the rollers results in abetter load distribution and lower forces on the guiding rail.

The point of attack of the operating forces for opening and closing doesnot need to be centered between the two hinges; the allowable tolerancefor an asymmetric push or pull force is much wider.

The guidance perpendicular to the movement plane is improved during thelongitudinal movement.

The radome cover opening kinematic requires less space in lengthcompared to state-of-the-art solutions with a rod and a guiding tube,because there is no remaining rod length necessary behind the hingepoint as in those state-of-the-art solutions.

The operation of the radome cover opening kinematic is improved at veryhigh or very low temperatures compared to state-of-the-art solutions.

The radome cover opening kinematic is less susceptible to dirt and dust.The motion link with the attached movable part can easily bedisassembled and reinstalled from the guiding rail without need foradjustment.

According to one aspect, the aircraft further comprises a radome coverattachment surface that is attached to the radome cover openingkinematic and receives the radome cover shell.

According to one aspect, the aircraft further comprises a roller bearingbracket that is attached to the aircraft structure and receives the atleast three rollers.

According to one aspect, the aircraft further comprises a plurality oflatches that are adapted to maintain the radome cover shell in theclosed position.

According to one aspect, a latch of the plurality of latches furthercomprises an eye that is attached to the radome cover shell; a latchhook that engages with the eye in the closed position; and a biasingdevice that biases the latch hook to stay engaged with the eye.

According to one aspect, the latch of the plurality of latches furthercomprises an alignment pin and an alignment fork, wherein the alignmentpin and the alignment fork guide the eye towards the latch hook duringat least a portion of the second movement of the radome cover shell fromthe opened position to the closed position.

According to one aspect, the guiding rail further comprises a curved endthat engages with the first roller to form a guiding rail rear stopperthat stops the longitudinal movement of the radome cover shell at thefirst partially opened position.

According to one aspect, the first roller defines a rotation axis aroundwhich the radome cover shell rotates during the first and secondrotational movements of the radome cover shell.

According to one aspect, the aircraft further comprises a roller guidethat is attached to the radome cover shell, wherein at least the thirdroller of the at least three rollers is arranged between the guidingrail and the roller guide when the radome cover shell is in the closedposition.

According to one aspect, the roller guide further comprises a firstportion that is parallel to the guiding rail; and a second portion thatis kinked away from the guiding rail at a predetermined angle.

According to one aspect, the third roller is in contact with the secondportion of the roller guide during the first rotational movement of theradome cover shell.

According to one aspect, the roller guide is removed from the thirdroller during the second rotational movement of the radome cover shell.

According to one aspect, the aircraft further comprises a rod having afirst and a second end, wherein the first end is attached to theaircraft structure; and a rod holder bracket that is mounted on theradome cover shell and adapted to receive the second end of the rod whenthe radome cover shell is in the completely opened position.

According to one aspect, the aircraft further comprises a rod retainerbracket that is mounted on the aircraft structure and adapted to receivethe second end of the rod when the radome cover shell is in the closedposition.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments are outlined by way of example in the following descriptionwith reference to the attached drawings. In these attached drawings,identical or identically functioning components and elements are labeledwith identical reference numbers and characters and are, consequently,only described once in the following description.

FIG. 1 shows a perspective view of an illustrative aircraft having aradome with a radome cover that includes a radome cover shell and aradome cover opening kinematic in accordance with some embodiments,

FIG. 2A is a diagram of an illustrative radome cover with a radome covershell and a radome cover opening kinematic in a closed position inaccordance with some embodiments,

FIG. 2B is a diagram of an illustrative radome cover with a radome covershell and a radome cover opening kinematic at the end of a longitudinalmovement from the closed position of FIG. 2A to a first partially openedposition in accordance with some embodiments,

FIG. 2C is a diagram of an illustrative radome cover with a radome covershell and a radome cover opening kinematic during a first rotationalmovement from the first partially opened position of FIG. 2B to a secondpartially opened position in accordance with some embodiments,

FIG. 2D is a diagram of an illustrative radome cover with a radome covershell and a radome cover opening kinematic during a second rotationalmovement from the second partially opened position to a completelyopened position in accordance with some embodiments,

FIG. 3 shows an isometric view of an illustrative radome cover with aradome cover, a radome cover opening kinematic, latches, locks, a rod,and a rod holder bracket in accordance with some embodiments,

FIG. 4 shows a three-dimensional view of a portion of an illustrativeradome cover opening kinematic in accordance with some embodiments,

FIG. 5 shows a three-dimensional view of the inside of an illustrativeradome cover having a radome cover opening kinematic and a radome covershell in the closed position in accordance with some embodiments,

FIG. 6A shows a three-dimensional view of an illustrative radome coveropening kinematic when a corresponding radome cover shell is in theclosed position in accordance with some embodiments,

FIG. 6B shows a three-dimensional view of the illustrative radome coveropening kinematic of FIG. 6A at the end of a longitudinal movement fromthe closed position of FIG. 6A to a first partially opened position ofthe radome cover shell in accordance with some embodiments,

FIG. 6C shows a three-dimensional view of the illustrative radome coveropening kinematic of FIG. 6B during a rotational movement from the firstpartially opened position of FIG. 6B to a completely opened position ofthe radome cover shell in accordance with some embodiments,

FIG. 6D shows a three-dimensional view of an illustrative radome coverwith a radome cover shell attached to the radome cover opening kinematicof FIG. 6C with the radome cover shell being in the completely openedposition in accordance with some embodiments,

FIG. 7A is a diagram of a portion of an illustrative lower latch andlock mechanism for a radome cover visible at the inside of the radomecover in accordance with some embodiments,

FIG. 7B is a diagram of the portion of the illustrative lower latch andlock mechanism of FIG. 7A visible at the outside of the radome cover inaccordance with some embodiments, and

FIG. 8 is a diagram of an illustrative upper latch and lock mechanismfor a radome cover visible at the inside of the radome cover inaccordance with some embodiments.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1 shows an aircraft 100 with an aircraft airframe 102, which issometimes also referred to as fuselage 102. Illustratively, aircraft 100is an airplane. However, the present embodiments are not limited toairplanes. Instead, any vehicle with a radome such as a verticaltake-off and landing (VTOL) aircraft, a helicopter, a drone, etc. islikewise contemplated.

If desired, the aircraft 100 is accessible via a plurality of aircraftdoors 104, which exemplarily comprises several cabin access doors 104 a,104 b, 104 c and 104 d, as well as one or more cargo deck access doors104 e.

The plurality of aircraft doors 104 may be adapted to close the aircraftairframe 102 (i.e., fuselage 102 of the aircraft 100) in a fluid-tightmanner.

Fuselage 102 may include an aircraft structure 103 and an aircraft skin109 that is attached to aircraft structure 103. As an example, aircraft100 may include a radome with a radome cover located at the nose regionof aircraft 100. The radome cover may include a radome cover shell 112and a radome cover opening kinematic. The radome cover shell 112 may bea part of aircraft skin 109.

If desired, radome cover shell 112 may enclose equipment 115 in the noseregion 110 of the aircraft 100. For example, radome cover shell 112 mayenclose equipment 115 such as radar antennas, if desired.

FIG. 2A is a diagram of an illustrative radome cover with a radome coveropening kinematic 200 and a radome cover shell 112 in a closed position.The radome cover shell 112 is adapted to enclose equipment 115 in a noseregion of an aircraft (e.g., nose region 110 of aircraft 100 of FIG. 1 )in the closed position shown in FIG. 2A.

Illustratively, radome cover opening kinematic 200 may include guidingrail 210 and at least three rollers 230. If desired, radome coveropening kinematic 200 may include roller guide 220. Roller guide 220 mayinclude a first portion 222 that is parallel to the guiding rail 210. Ifdesired, roller guide 220 may include a second portion 224 that iskinked away from the guiding rail 210 at a predetermined angle.

As shown in FIGS. 2A to 2D, radome cover opening kinematic 200 mayinclude three rollers 230 a, 230 b, 230 c. However, radome cover openingkinematic 200 may include more than three rollers, if desired. As anexample, radome cover opening kinematic 200 may include additionalrollers between rollers 230 b and 230 c.

By way of example, guiding rail 210 and roller guide 220 may both beattached to radome cover shell 112. The at least three rollers 230 maybe attached to aircraft structure 103.

Illustratively, a first and a second roller 230 a, 230 b of the at leastthree rollers 230 may be arranged on opposing sides of the guiding rail210. The second and a third roller 230 b, 230 c of the at least threerollers 230 may be arranged on the same side of the guiding rail 210.

At least the third roller 230 c may be located between guiding rail 210and the first portion 222 of roller guide 220 during a longitudinalmovement of the radome cover shell 112 from the closed position shown inFIG. 2A to a first partially opened position shown in FIG. 2B. Thus, thefirst portion 222 of roller guide 220 and roller 230 c may prevent arotational movement of radome cover shell 112 while roller 230 c isbetween guiding rail 210 and the first portion 222 of roller guide 220(i.e., during the longitudinal movement of radome cover shell 112).

Guiding rail 210 may have a straight portion to enable a longitudinalmovement of the radome cover shell 112 along the plurality of rollers230. If desired, guiding rail 210 may include a curved end 215. Curvedend 215 may engage with first roller 230 a to form a guiding rail rearstopper 217 that stops the longitudinal movement of the radome covershell 112 at the first partially opened position.

Placing rollers 230 a and 230 b opposing each other on opposing sides ofguiding rail 210 may prevent a rotational movement of radome cover shell112 until curved end 215 engages with first roller 230 a.

FIG. 2B is a diagram of an illustrative radome cover with radome coveropening kinematic 200 and radome cover shell 112 at the end of thelongitudinal movement from the closed position of FIG. 2A to a firstpartially opened position in accordance with some embodiments.

As shown in FIG. 2B, curved end 215 engages with the first roller 230 ato form guiding rail rear stopper 217. Guiding rail rear stopper 217(i.e., curved end 215 together with roller 230 a) stops the longitudinalmovement of the radome cover shell 112 at the first partially openedposition and prevents any further longitudinal movement of radome covershell 112.

In the first partially opened position, roller 230 c is no longerlocated between guiding rail 210 and the first portion 222 of rollerguide 220. Thus, roller 230 c may no longer prevent a rotationalmovement of radome cover shell 112 around an axis defined by roller 230a (i.e., a counterclockwise rotation of radome cover shell 112 aroundroller 230 a as shown in FIG. 2B) in the first partially openedposition. However, roller 230 c still prevents a rotational movement ofradome cover shell 112 around an axis defined by roller 230 b (i.e., aclockwise rotation of radome cover shell 112 around roller 230 b asshown in FIG. 2B) in the first partially opened position.

In fact, upon reaching the first partially opened position, radome covershell 112 is free to perform a first rotational movement from the firstpartially opened position to a second partially opened position asillustrated in FIG. 2C.

As shown in FIG. 2C, roller 230 a defines a rotation axis around whichradome cover shell 112 rotates during the first rotational movement ofradome cover shell 112. If desired, roller 230 c may be in contact withthe second portion 224 of roller guide 220 at least during a portion ofthe first rotational movement from the first partially opened positionto the second partially opened position of radome cover shell 112.

In other words, roller 230 a and curved end 215 may at least in partdefine the first rotational movement of radome cover shell 112, and thesecond portion 224 of roller guide 220 and roller 230 c may support thedefinition of the first rotational movement of radome cover shell 112.If desired, the second portion 224 of roller guide 220 together withroller 230 c may guide the radome cover shell 112 during a closingmovement between the second partially opened position and the firstpartially opened position.

If desired, radome cover shell 112 may perform a second rotationalmovement from the second partially opened position to a completelyopened position. FIG. 2D shows radome cover shell 112 in the completelyopened position.

Illustratively, roller 230 c may not be in contact with the secondportion 224 of roller guide 220 during the second rotational movement.If desired, the radome shell opening kinematic 210 may include a radomecover shell rotation stopper that stops the second rotational movementof the radome cover shell 112 at the completely opened position.

FIG. 3 shows an isometric view of an illustrative radome cover. Theradome cover may include radome cover shell 112, radome cover openingkinematic 200, and latches and/or locks 300. If desired, the radomecover may include one or more rods 410 and corresponding one or more rodholder brackets 420 to maintain the radome cover shell 112 in thecompletely opened position.

Latches and/or locks 300 may be adapted to maintain radome cover shell112 in the closed position. Illustratively, a latch and/or lock 300 mayinclude an eye that is attached to radome cover shell 112 and a latchhook that is attached to an aircraft structure (e.g., aircraft structure103 of FIG. 1 ). If desired, the eye of latch and/or lock 300 may beattached to the aircraft structure, while the latch hook is attached tothe radome cover shell 112.

The latch hook may engage with the eye in the closed position of radomecover shell 112. The illustrative latch and/or lock 300 may include analignment pin and/or an alignment fork 340. The alignment pin and/or thealignment fork 340 may guide the eye towards the latch hook during atleast a portion of the second movement of the radome cover shell 112from the opened position to the closed position.

If desired, the latch and/or lock may include a biasing device thatbiases the latch hook to stay engaged with the eye. For example, thebiasing device may include a spring.

During the movement of the radome cover shell 112 from an opened to theclosed position, the eye may push the latch hook from its biasedposition against the force of the spring. When the radome cover shell112 has reached the closed position, the spring may push the latch hookback into its biased position in which it engages with the eye tomaintain the radome cover shell 112 in its closed position.

If desired, latch and/or lock 300 may include release push button 350and/or unlatch handle 360. Release push button 350 and/or unlatch handle360 may be adapted to disengage the latch hook from the eye. Forexample, release push button 350 and/or unlatch handle 360 may pushagainst the force of the biasing device and move the latch hook from itsbiased position.

As shown in FIG. 3 , the radome cover may include four latches and/orlocks 300. If desired, the radome cover may have a different number oflatches and/or locks 300. For example, the radome cover may include one,two, three, five, six, or any other number of latches and/or locks 300.Latches and/or locks 300 are described in more detail in FIGS. 7A, 7B,and 8 .

By way of example, the radome cover may include one or more openinghandles 380. The one or more opening handles 380 may be adapted toprovide a handle to an operator who moves the radome cover shell 112from the closed to an opened position and/or from the opened to theclosed position.

By way of example, the one or more rods 410 may have a first end 412 anda second end 415. The second end 415 of rod 410 may be attached to theaircraft structure 103.

The corresponding one or more rod holder brackets 420 may be mounted tothe radome cover shell 112 and adapted to receive the respective secondends 415 of the corresponding rods 410 when the radome cover shell 112is in the completely opened position. Thereby, the one or more rods 410and the corresponding one or more rod holder brackets 420 may maintainthe radome cover shell 112 in the completely opened position.

If desired, one or more rod retainer brackets 430 may be mounted on theaircraft structure 103. The one or more rod retainer brackets 430 may beadapted to receive the respective second ends 415 of the correspondingrods 410 when the radome cover shell 112 is in the closed position.Thereby, the respective second ends 415 of rods 410 may be safely stowedaway when the radome cover shell 112 is in the closed position.

Illustratively, a roller bearing bracket 250 may be attached to theaircraft structure 103. The roller bearing bracket 250 is described inmore detail in FIG. 4 .

FIG. 4 shows a three-dimensional view of a portion of an illustrativeradome cover opening kinematic 200 with a roller bearing bracket 250 inaccordance with some embodiments.

Roller bearing bracket 250 may receive at least three rollers 230 suchas rollers 230 a, 230 b, and 230 c. Illustratively, roller bearingbracket 250 may receive guiding rail rear stopper 217. Thus, theportions of the radome cover opening kinematic 200 that are attached tothe roller bearing bracket 250 may be quickly and easily replacement byreplacing the roller bearing bracket 250 with all attached parts.

Illustratively, roller bearing bracket 250 may be closed to preventwater penetration and thereby reduce the risk of corrosion. If desired,roller bearing bracket 250 may be inclined for drainage so that watercannot accumulate, thereby further reduce the risk of corrosion.

By way of example, roller bearing bracket 250 may include a frame thatencompasses a truss. The truss may include a plurality of beams toprovide for increased stability. Roller 230 c may be mounted to theframe, if desired. A beam may connect rollers 230 b and 230 c, andanother beam may connect rollers 230 a and 230 b.

The frame may have the shape of an irregular hexagon. At least somevertices of the hexagon may have first reinforcements. The firstreinforcements may protrude towards the inside of the frame.

Illustratively, roller bearing bracket 250 may have secondreinforcements at least in some locations in which beams of the trussintersect with each other. First and second reinforcements may have anyshape. For example, reinforcements may be round, triangular,rectangular, etc.

If desired, roller bearing bracket 250 may be attached with the aircraftstructure through at least some of the vertices of the frame and/orthrough some of the first and/or second reinforcements.

FIG. 5 shows a three-dimensional view of the inside of an illustrativeradome cover having a radome cover opening kinematic and a radome covershell in the closed position in accordance with some embodiments.

The illustrative radome cover may include a radome cover attachmentsurface 240. Radome cover attachment surface 240 may be attached to theradome cover opening kinematic 200. If desired, the radome coverattachment surface 240 may receive the radome cover shell 112.

As an example, radome cover attachment surface 240 may include boreholes 242 and radome cover shell 112 may be attached to radome coverattachment surface 240 with fasteners that attach with bore holes 242.

Any type of fasteners may be used to attach radome cover shell 112 toradome cover attachment surface 240. Fasteners may include screws, boltsand nuts, pins, rivets, nails, clips, clamps, brackets, or any othertype of fastener that may be suitable to attach radome cover shell 112to radome cover attachment surface 240. If desired, radome cover shell112 may be soldered and/or glued to radome cover attachment surface 240.

Radome cover opening kinematic 200 may include guiding rail 210. Guidingrail 210 may be straight and have a curved end 215. As shown in FIG. 5 ,guiding rail 210 may have a U-shaped profile and at least one roller ofthe plurality of rollers 230 (e.g., roller 230 a) may move within theU-shaped profile.

If desired, guiding rail 210 may have an H-shaped profile and allrollers of the plurality of rollers 230 (e.g., rollers 230 a, 230 b, 230c) may move on either side of the guiding rail 210 within the H-shapedprofile.

Illustratively, radome cover opening kinematic 200 may include rollerguide 220. Roller guide 220 may have a first portion 222 that isparallel to the guiding rail 210 and a second portion 224 that is kinkedaway from the guiding rail 210 at a predetermined angle.

If desired, the first portion 222 and/or the second portion 224 ofroller guide 220 may have a U-shaped profile. By way of example, atleast one roller of the plurality of rollers 230 (e.g., roller 230 c)may move within the U-shaped profile.

As shown in FIG. 5 , the illustrative radome cover may include a latchand/or lock 300 that is adapted to maintain radome cover shell 112 inthe closed position. Illustratively, the latch and/or lock 300 mayinclude an eye 310 that is attached to radome cover shell 112.

A latch hook 320 may be attached to the aircraft structure. The latchhook 320 may engage with the eye 310 in the closed position. If desired,latch hook 320 may be attached to radome cover shell 112 and eye 310 tothe aircraft structure.

FIG. 6A shows a three-dimensional view of an illustrative radome coveropening kinematic when a corresponding radome cover shell (e.g., radomecover shell 112 of FIGS. 1 to 3 ) is in the closed position inaccordance with some embodiments.

Illustratively, roller bearing bracket 250 may have a plate to which thetruss of FIG. 4 may be attached. If desired, roller bearing bracket 250may be attached with the aircraft structure through the plate.

Roller bearing bracket 250 may be at least partially made of compositematerial. If desired, roller bearing bracket 250 may be at leastpartially made of metal.

As shown in FIG. 6A, radome cover attachment surface 240 may be attachedto the radome cover opening kinematic 200. If desired, radome coverattachment surface 240 may include bore holes 242 and a radome covershell may be attached to radome cover attachment surface 240 withfasteners that attach with bore holes 242.

FIG. 6B shows a three-dimensional view of the illustrative radome coveropening kinematic of FIG. 6A at the end of a longitudinal movement fromthe closed position of FIG. 6A to a first partially opened position ofthe radome cover shell in accordance with some embodiments.

As shown in FIG. 6B, curved end 215 of guiding rail 210 engages with thefirst roller 230 a to form guiding rail rear stopper 217. Guiding railrear stopper 217 (i.e., curved end 215 together with roller 230 a) stopsthe longitudinal movement of the radome cover shell at the firstpartially opened position and prevents any further longitudinal movementof the radome cover shell other than a longitudinal movement backtowards the closed position of FIG. 6A.

If desired, guiding rail rear stopper 217 may include roller 230 b inaddition to curved end 215 and roller 230 a. Thus, guiding rail rearstopper 217 may prevent any movement that is different than a rotationalmovement around an axis defined by roller 230 a or a longitudinalmovement of the radome cover shell towards the closed position of FIG.6A.

Upon reaching the first partially opened position, the radome covershell is free to perform a rotational movement.

FIG. 6C shows a three-dimensional view of the illustrative radome coveropening kinematic of FIG. 6B during a rotational movement from the firstpartially opened position of FIG. 6B to a completely opened position ofthe radome cover shell in accordance with some embodiments.

At the completely opened position, radome cover shell rotation stopper260 stops the second rotational movement of the radome cover shell. Forexample, during the second rotational movement, guiding rail 210 mayreach radome cover shell rotation stopper 260, which may prevent guidingrail 210 from performing any further rotational movement.

FIG. 6D shows a three-dimensional view of an illustrative radome coverwith a radome cover shell attached to the radome cover opening kinematicof FIG. 6C with the radome cover shell being in the completely openedposition in accordance with some embodiments.

As shown in FIG. 6D, the radome cover may include at least two latchesand/or locks 300. Latches and/or locks 300 are described in more detailin FIGS. 7A, 7B, and 8 .

By way of example, the radome cover may include one or more openinghandles 380. The one or more opening handles 380 may be adapted toprovide a grip to an operator that moves the radome cover shell 112 fromthe closed to an opened position and/or from the opened to the closedposition.

FIG. 7A is a diagram of a portion of an illustrative lower latch and/orlock for a radome cover visible at the inside of the radome cover inaccordance with some embodiments.

As shown in FIG. 7A, portion 305 of latch and/or lock 300 may includelatch hook 320, biasing device 330, alignment fork 340, unlatch handle360, and release hook 370. Latch and/or lock 300 may include portion 305of latch and/or lock 300 and a counterpart portion of latch and/or lock300. Latch and/or lock 300 may be adapted to maintain radome cover shell112 in a closed position.

Portion 305 of latch and/or lock 300 may be attached to radome covershell 112 and the counterpart portion of latch and/or lock 300 may beattached to an aircraft structure (e.g., aircraft structure 103 of FIG.1 ). If desired, portion 305 of latch and/or lock 300 may be attached tothe aircraft structure and the counterpart portion of latch and/or lockmay be attached to radome cover shell 112.

Illustratively, the counterpart portion of latch and/or lock 300 mayinclude an eye. Portion 305 of latch and/or lock 300 may be adapted toreceive the eye. For example, latch hook 320 may engage with the eye inthe closed position.

If desired, portion 305 of latch and/or lock 300 may include a biasingdevice 330. Biasing device 330 may bias latch hook 320 into apredetermined position. For example, biasing device 330 may bias latchhook 320 to stay engaged with the eye.

The outside of latch hook 320 may be shaped such that the eye is able tomove latch hook 320 out of the biased position during the move of radomecover shell 112 into the closed position. For example, the outside oflatch hook 320 may have a kink.

By way of example, biasing device 330 may include a spring that pusheslatch hook 320 in direction of alignment fork 340. Unlatch handle 360may be adapted to move latch hook 320 out of the biased position toenable the release of the eye from latch hook 320. Thus, unlatch handle360 may push directly or indirectly against biasing device 330 and/oragainst latch hook 320 such that latch hook 320 is moved out of thebiased position.

Release hook 370 may block unlatch handle 360 when latch and/or lock 300is locked. Release hook 370 may allow unlatch handle 360 to unlatchlatch and/or lock 300 when latch and/or lock 300 is unlocked. In otherwords, release hook 370 may cause a transition of latch and/or lock 300from a locked state to an unlocked state and vice versa.

Alignment fork 340 may guide the eye towards the latch hook 320 duringthe movement of the radome cover shell 112 to the closed position. Forexample, the counterpart portion of latch and/or lock 300 may include apin that is oriented perpendicular to alignment fork 340 and alignmentfork 340 may receive the pin between the two prongs of alignment fork340.

FIG. 7B is a diagram of the portion of the illustrative lower latch andlock mechanism of FIG. 7A visible at the outside of the radome cover inaccordance with some embodiments. As shown in FIG. 7B, portion 305 oflatch and/or lock 300 may include latch hook 320, alignment fork 340,release push button 350, and unlatch handle 360.

Illustratively, release push button 350 may act on release hook 370. Asan example, release push button 350 may cause release hook 370 to blockunlatch handle 360 when latch and/or lock 300 is in the unlocked state,thereby transitioning latch and/or lock 300 into the locked state. Asanother example, release push button 350 may cause release hook 370 toallow unlatch handle 360 to unlatch latch and/or lock 300 when latchand/or lock 300 is in the locked state, thereby transitioning latchand/or lock 300 into the unlocked state.

When latch and/or lock 300 is in the unlocked state, unlatch handle 360may be adapted to move latch hook 320 out of the biased position toenable the release of the eye from latch hook 320.

FIG. 8 is a diagram of an illustrative upper latch and lock mechanismfor a radome cover visible at the inside of the radome cover inaccordance with some embodiments. FIG. 8 shows latch and/or lock 300 ina closed state. In the closed state, latch hook 320 has latched onto eye310. Thus, latch and/or lock 300 maintains radome cover in a closedstate.

Illustratively, release push button 350 may act on a release hook thatis adapted to block unlatch handle 360. For example, release push button350 may cause the release hook to allow unlatch handle 360 to unlatchlatch and/or lock 300 when latch and/or lock 300 is in the locked state.In other words, release push button 350 may via the release hook cause atransition of latch and/or lock 300 from a locked state to an unlockedstate.

If desired, release push button 350 may cause the release hook to blockunlatch handle 360 when latch and/or lock 300 is in the unlocked state.In other words, release push button 350 may via the release hook cause atransition of latch and/or lock 300 from an unlocked state to a lockedstate.

Latch and/or lock 300 may include alignment pin 840. Alignment pin 840may guide the eye 310 towards the latch hook 320 during the movement ofa radome cover shell from the opened position to the closed position.

For example, alignment pin 840 may be located on one portion of latchand/or lock 300 (e.g., on portion 305 of lock and/or latch 300 of FIGS.7A and 7B). A funnel may be located on the counterpart portion of latchand/or lock 300. The funnel may together with the alignment pin 840guide the eye 310 towards the latch hook 320, if desired.

Illustratively, latch and/or lock 300 may have an alignment fork. Ifdesired, alignment pin 840 and the alignment fork may both guide the eye310 towards the latch hook 320 during the movement of the radome covershell from the opened position to the closed position.

It should be noted that modifications to the above described embodimentsare within the common knowledge of the person skilled in the art and,thus, also considered as being part of the present invention.

For instance, latch and/or lock 300 of FIG. 7A is shown with a latchhook 320 that engages with an eye in the closed position of radome covershell 112. However, any other device that engages with an eye in theclosed position is likewise contemplated. For example, latch and/or lock300 may include a pair of pliers instead of a latch hook 320. The pairof pliers may have a slot that may engage with the eye. Moreover, thebiasing device 330 of FIG. 7A may push the prongs of the pair of plierstogether instead of pushing latch hook 320 in direction of alignmentfork 340.

Furthermore, the second portion 224 of roller guide 220 is shown inFIGS. 6A to 6D as comprising a rectangular sheet without any sidewalls.However, the second portion 224 of roller guide 220 may have atrapezoidal shape with the shorter of the two parallel sides beingattached to the first portion 222 of roller guide 220. Moreover, thesecond portion 224 of roller guide 220 may have sidewalls. The sidewallsmay assist in guiding the movement of radome cover shell 112 from thecompletely opened position to the closed position.

REFERENCE LIST

-   100 aircraft-   102 aircraft airframe, fuselage-   103 aircraft structure-   104 aircraft door-   104 a, 104 b, 104 c, 104 d cabin access doors-   104 e cargo deck access door-   109 aircraft skin-   110 nose region-   112 radome cover shell-   115 equipment-   200 radome cover opening kinematic-   210 guiding rail-   215 curved end-   217 guiding rail rear stopper-   220 roller guide-   222 first portion-   224 second portion-   230 plurality of rollers-   230 a, 230 b, 230 c roller-   240 radome cover attachment surface-   242 bore holes-   250 roller bearing bracket-   260 radome cover shell rotation stopper-   300 latch, lock-   305 latch and/or lock portion-   310 eye-   320 latch hook-   330 biasing device-   340 alignment fork-   350 release push button-   360 unlatch handle-   370 release hook-   380 opening handle-   410 rod-   412 first end-   415 second end-   420 rod holder bracket-   430 rod retainer bracket-   840 alignment pin.

What is claimed is:
 1. An aircraft with an aircraft structure,comprising: a radome cover shell that is adapted to enclose equipment ina nose region of the aircraft in a closed position; and a radome coveropening kinematic that enables a first movement of the radome covershell from the closed position to an opened position and a secondmovement of the radome cover shell from the opened position to theclosed position, wherein the radome cover opening kinematic comprises: aguiding rail that is attached to the radome cover shell, and at leastthree rollers that are attached to the aircraft structure, wherein afirst and a second roller of the at least three rollers are arranged onopposing sides of the guiding rail, and wherein the second and a thirdroller of the at least three rollers are arranged on the same side ofthe guiding rail, wherein the first movement of the radome cover shellfrom the closed position to the opened position comprises a longitudinalmovement from the closed position to a first partially opened position,a first rotational movement from the first partially opened position toa second partially opened position, and a second rotational movementfrom the second partially opened position to the opened position,wherein the radome shell opening kinematic further comprises: a radomecover shell rotation stopper that stops the second rotational movementof the radome cover shell at the opened position.
 2. The aircraft ofclaim 1, further comprising: a radome cover attachment surface that isattached to the radome cover opening kinematic and receives the radomecover shell.
 3. The aircraft of claim 1, further comprising: a rollerbearing bracket that is attached to the aircraft structure and receivesthe at least three rollers.
 4. The aircraft of claim 1, furthercomprising: a plurality of latches that are adapted to maintain theradome cover shell in the closed position.
 5. The aircraft of claim 4,wherein a latch of the plurality of latches further comprises: an eyethat is attached to the radome cover shell; a latch hook that engageswith the eye in the closed position; and a biasing device that biasesthe latch hook to stay engaged with the eye.
 6. The aircraft of claim 5,wherein the latch of the plurality of latches further comprises: analignment pin; and an alignment fork, wherein the alignment pin and thealignment fork guide the eye towards the latch hook during at least aportion of the second movement of the radome cover shell from the openedposition to the closed position.
 7. The aircraft of claim 1, wherein theguiding rail further comprises: a curved end that engages with the firstroller to form a guiding rail rear stopper that stops the longitudinalmovement of the radome cover shell at the first partially openedposition.
 8. The aircraft of claim 7, wherein the first roller defines arotation axis around which the radome cover shell rotates during thefirst and second rotational movements of the radome cover shell.
 9. Theaircraft of claim 7, further comprising: a roller guide that is attachedto the radome cover shell, wherein at least the third roller of the atleast three rollers is arranged between the guiding rail and the rollerguide when the radome cover shell is in the closed position.
 10. Theaircraft of claim 9, wherein the roller guide further comprises: a firstportion that is parallel to the guiding rail; and a second portion thatis kinked away from the guiding rail at a predetermined angle.
 11. Theaircraft of claim 10, wherein the third roller is in contact with thesecond portion of the roller guide during the first rotational movementof the radome cover shell.
 12. The aircraft of claim 10, wherein theroller guide is removed from the third roller during the secondrotational movement of the radome cover shell.
 13. The aircraft of claim1, further comprising: a rod having a first and a second end, whereinthe first end is attached to the aircraft structure; and a rod holderbracket that is mounted on the radome cover shell and adapted to receivethe second end of the rod when the radome cover shell is in the openedposition.
 14. The aircraft of claim 13, further comprising: a rodretainer bracket that is mounted on the aircraft structure and adaptedto receive the second end of the rod when the radome cover shell is inthe closed position.
 15. An aircraft with an aircraft structure, theaircraft comprising: a radome cover shell movable between a closedposition and an opened position, the radome cover shell capable ofenclosing equipment in a nose region of the aircraft in the closedposition; and a radome cover opening kinematic that enables movement ofthe radome cover shell between the closed position and the openedposition, wherein the radome cover opening kinematic comprises: aguiding rail attached to the radome cover shell, and at least threerollers attached to the aircraft structure, a first roller of the atleast three rollers arranged on a first side of the guiding rail, and asecond roller and a third roller of the at least three rollers arrangedon a second side of the guiding rail, wherein the radome shell openingkinematic further comprises: a radome cover shell rotation stoppercapable of stopping movement of the radome cover shell at the openedposition; further comprises a plurality of latches that are adapted tomaintain the radome cover shell in the closed position; and whereinmovement of the radome cover shell from the closed position to theopened position comprises a first movement from the closed position to afirst partially opened position, a second movement from the firstpartially opened position to a second partially opened position, and athird movement from the second partially opened position to the openedposition such that the opened position comprises the opened position.16. The aircraft of claim 15, further comprising: a radome coverattachment surface attached to the radome cover opening kinematiccapable of receiving the radome cover shell.
 17. The aircraft of claim15, further comprising: a roller bearing bracket attached to theaircraft structure and receiving the at least three rollers.
 18. Anaircraft comprising: an aircraft structure having a nose region; aradome cover shell adapted to be able to enclose equipment in the noseregion of the aircraft in a closed position; and a radome cover openingkinematic that enables a first movement of the radome cover shell fromthe closed position to an opened position and a second movement of theradome cover shell from the opened position to the closed position,wherein the radome cover opening kinematic comprises: a guide attachedto the radome cover shell, and at least three rollers attached to theaircraft structure, wherein a first roller and a second roller of the atleast three rollers are arranged on opposing sides of the guide, andwherein the second roller and a third roller of the at least threerollers are arranged on the same side of the guide, wherein the firstmovement of the radome cover shell from the closed position to theopened position comprises a longitudinal movement from the closedposition to a first partially opened position, a first rotationalmovement from the first partially opened position to a second partiallyopened position, and a second rotational movement from the secondpartially opened position to the opened position, wherein the radomeshell opening kinematic further comprises: a radome cover shell rotationstopper that stops the second rotational movement of the radome covershell at the opened position.
 19. The aircraft of claim 18, furthercomprising: a plurality of latches that are adapted to maintain theradome cover shell in the closed position.